CN107860504A - The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine - Google Patents
The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine Download PDFInfo
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- CN107860504A CN107860504A CN201710936008.2A CN201710936008A CN107860504A CN 107860504 A CN107860504 A CN 107860504A CN 201710936008 A CN201710936008 A CN 201710936008A CN 107860504 A CN107860504 A CN 107860504A
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- demarcation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L25/00—Testing or calibrating of apparatus for measuring force, torque, work, mechanical power, or mechanical efficiency
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- Force Measurement Appropriate To Specific Purposes (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
In order to solve the technical problem that current stable state thrust performance measurement can not be realized with dynamic thrust feature measurement simultaneously, the invention provides a kind of Quasi dynamic thrust measurement of attitude control engine to calibrate integrated apparatus, including determines frame, mounting seat, sensor cluster, changeover module, demarcation component, charge amplifier, cylinder control, acquisition system and data handling system；The changeover module includes the switching cylinder, switching ring and sensor pull rod to connect successively；The one end for switching ring is connected with switching the air cylinder tie rod of cylinder, switches the other end of ring and one end pivot bush unit of sensor pull rod；The other end of sensor pull rod is threadedly coupled with the newel of the strain transducer at newel screwed hole；Switch cylinder action and drive switching ring motion so that switching ring departs from or tensed with sensor pull rod, realizes the switching of strain transducer and piezoelectric transducer, so as to carry out attitude control engine dynamic, the measurement of stable state thrust performance simultaneously in a measurement apparatus.
Description
Technical field
The invention belongs to space flight liquid engine experimental technique field, is related to a kind of attitude control engine Quasi dynamic thrust measurement
Calibrate integrated apparatus.
Background technology
The mode of operation of attitude control engine is divided into the work of long-range and short time impulse form, wherein short time impulse form
Pattern is to carry out the premise of exact posture control.Technical merit and attitude control engine Development Techniques yet with measurement sensor
Limitation, the leading indicator of conventional attitude control engine thrust performance is stable state thrust level.But with the development of Development Techniques, by
Walk and requirement is proposed to the dynamic characteristic measuring precision of attitude control engine thrust.
At present, it is widely used in strain force sensor stable state thrust measurement at home and abroad field, its major advantage is
Simple in construction, easy to use, stable performance, reliability are high；It was easily achieved process automation and Multipoint synchronous measurement, remote survey
Amount；High sensitivity, response speed are also higher；Static accuracy is high；Low internal resistance output；Anti-interference is good；Technique for applying technology is more
It is ripe.But the shortcomings that strain force sensor is that dynamic response is relatively poor, it is necessary to subsequently be carried out to dynamic measurement parameter attached
Add processing.
For piezoelectric transducer using more in dynamic thrust measuring system, its major advantage is that dynamic characteristic is good, rigidity
High, achievable non-displacement measurement.But due to the drift of charge inducing, its static accuracy is relatively low, to Steady-state Parameters required precision not
Gao Shike carries out the quasistatic measurement of short time, but can not be carried out for prolonged steady state measurement.
Although as the raising of manufacturing technology, the rigidity and dynamic response capability of strain transducer itself have obtained constantly carrying
Height, the small piezoelectric transducer development of drift value also make some progress, but fail to see one kind can carry out simultaneously compared with
High-precision stable state thrust and the device of dynamic thrust measurement, to meet to protect while dynamic thrust feature measurement ability is improved
This market demand of the stable state thrust measure precision of card degree of precision.
The content of the invention
In order to solve the technical problem that current stable state thrust performance measurement can not be realized with dynamic thrust feature measurement simultaneously,
The invention provides a kind of attitude control engine Quasi dynamic thrust measurement to calibrate integrated apparatus.
The technical scheme is that：
The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine, it is characterized in that：Including determining frame 11, peace
Fill at seat 21, sensor cluster, changeover module, demarcation component, charge amplifier, cylinder control, acquisition system and data
Reason system；
It is described to determine frame 11 and be fixedly mounted in the mounting seat 21；The mounting seat 21, which is used to realize, determines frame 11 and attitude control hair
The connection of motivation test bay；
The sensor cluster includes being coaxially installed on the strain sensing for determining the homonymy of frame 11 by preceding mounting flange 28
Device 14 and piezoelectric transducer 15；Demarcation flange 13 before being provided with the stress surface of strain transducer 14, in strain transducer 14
Newel screwed hole 25 is offered on stem 26；Piezoelectric transducer 15 is arranged on the outside of the middle part of the preceding demarcation flange 13, pressure
The head of electric transducer 15 is provided with experiment pinboard 16；More anti-drop rods 17 are provided with demarcation flange 13 before described, this is anti-
De- bar 17 does not contact therebetween through corresponding anticreep hole on the experiment pinboard 16；The experiment pinboard 16
Outside carries out anticreep using the locking of locking nut 18, and locking nut 18 does not contact with experiment pinboard 16；
The changeover module includes the switching cylinder 8, switching ring 10 and sensor pull rod 19 to connect successively；The switching gas
Cylinder 8 is determined on frame 11 by switching cylinder mounting flange 7 installed in described, and is oppositely arranged with the sensor cluster；Switch ring
10 one end is connected with switching the air cylinder tie rod 20 of cylinder 8, switches the other end of ring 10 and one end activity of sensor pull rod 19
Socket；The newel 26 of the other end of sensor pull rod 19 and the strain transducer 14 screw thread at newel screwed hole 25 connects
Connect；
The component of demarcating includes the preceding demarcation flange 13, demarcates flange 5, demarcation cylinder mounting seat 23 afterwards, demarcates gas
Cylinder 1, standard force snesor 2 and Duo Gen support bars 22；Flange 5 is demarcated afterwards by rear mounting flange 29 installed in described to determine outside frame 11
Side, it is oppositely arranged with the preceding demarcation flange 13；Demarcate afterwards between flange 5 and preceding demarcation flange 13 and pass through more demarcation pull bars 9
It is connected；One end of the more support bars 22 is fixedly mounted on by the rear mounting flange 29 determines the outside of frame 11, and the other end is solid
Dingan County fills the demarcation cylinder mounting seat 23；Demarcation cylinder mounting seat 23 be arranged in parallel with the rear demarcation flange 5；Demarcate cylinder
1 is arranged in demarcation cylinder mounting seat 23；Standard force snesor 2 is arranged on the head of demarcation cylinder 1, and by demarcating drawstring 4
It is connected with the rear demarcation flange 5；
The cylinder control is used to control the switching cylinder 8 and demarcation cylinder 1 to act；
The charge amplifier is used for the charge data for receiving the piezoelectric transducer 15, and is output to the collection system
System；
The acquisition system is used for the output number for gathering the standard force snesor, strain transducer 14 and charge amplifier
According to；
The data that the data handling system gathers to acquisition system are handled, obtain attitude control engine stable state thrust and
Dynamic thrust.
Further, spring leaf 12 before being provided between above-mentioned preceding demarcation flange 13 and preceding mounting flange 28.
Further, it is provided with rear spring leaf 6 between above-mentioned rear demarcation flange 5 and rear mounting flange 29.
Further, gap is big between the end face of newel 26 of above-mentioned strain transducer 14 and the matrix 27 of strain transducer 14
In the deflection of the design maximum range of strain transducer, and it is less than deflection corresponding to overload protection pressure value.
Further, above-mentioned switching ring 10 is cylindrical shape, and its one end being socketed with sensor pull rod 19 offers 60 ° of inner cones
Hole 30；One end that sensor pull rod 19 is socketed with switching ring 10 has the conical surface being adapted with 60 ° of internal taper holes.
Further, the both ends of above-mentioned demarcation drawstring 4 by draw ring 3 respectively with standard force snesor 2 and rear standardization
Orchid 5 is connected.
Further, above-mentioned anti-drop rod 17 has 4, and the support bar 22 has 8.
Further, above-mentioned demarcation drawstring 4 is steel wire rope.
Further, it is above-mentioned to determine frame 11 and the mounting seat 21 is integrated part.
Beneficial effects of the present invention：
1st, the present invention realizes the measurement of stable state thrust performance and the switching of dynamic thrust feature measurement by changeover module, so as to
Realize attitude control engine dynamic, the measurement of stable state thrust performance simultaneously in a measurement apparatus.
2nd, the present invention considers that strain transducer is influenceed its measurement accuracy by external force and site environment and can declined, therefore
Live calibrated in situ is carried out first with demarcation cylinder and standard force snesor pair of strain sensors before measuring, to avoid live ring
Measurement error caused by border interference (such as Propellant Supply pipeline, measurement cable, vacuum environment and temperature etc.), realize ground and
Under vacuum simulated environment before and after engine test thrust-measuring device automatic calibration.
3rd, the present invention is using power source of the switching cylinder as changeover module, automatic using demarcating cylinder as stable state and demarcating
Load and execution mechanism, possess the automatic Calibration ability of live original position, and during experiment, switched according to different program purposes
Different measurement sensors realizes high-precision measurement data.Whole device uses stainless steel as matrix, around sensor
, can be suitable for the work high temperature corrosion adverse circumstances using water cooling plant.
Brief description of the drawings
Fig. 1 is the theory diagram of Quasi dynamic thrust measurement calibration integrated apparatus of the present invention；
Fig. 2 is the preferred structure schematic diagram of Quasi dynamic thrust-measuring device of the present invention；
Fig. 3 is the structural representation of changeover module of the present invention；
Fig. 4 is the structural representation of strain transducer of the present invention；
Fig. 5 is the structural representation of heat-proof device of the present invention；
Fig. 6 is sectional view at A-A in Fig. 5.
Label in figure：
1- demarcates cylinder, 2- standard force snesors, 3- draw rings, 4- demarcation drawstrings, demarcates flange after 5-, spring leaf after 6-,
7- switches cylinder mounting flange, 8- switching cylinders, 9- demarcation pull bars, 10- switching rings, and 11- determines frame, spring leaf before 12-, before 13-
Demarcate flange, 14- strain transducers, 15- piezoelectric transducers, 16- experiment pinboards, 17- anti-drop rods, 18- locking nuts, 19-
Sensor pull rod, 20- air cylinder tie rods, 21- mounting seats, 22- support bars, 23- demarcation cylinder mounting seats, 24- heat-proof devices, 25-
Newel screwed hole, 26- newels, 27- matrixes, mounting flange before 28-, mounting flange after 29-, 30- internal taper holes.
Embodiment
The invention will be further described below in conjunction with the accompanying drawings.
Referring to Fig. 1-3, the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine of the invention, including determine frame
11st, mounting seat 21, sensor cluster, changeover module, demarcation component, charge amplifier, cylinder control, acquisition system, number
According to processing system；
Determine frame 11 to be fixedly mounted in mounting seat 21；Determine frame 11 to be used to installing and supporting other each components；Mounting seat 21 is used
Determine the sub connection with test bay of frame 11 in realizing, and active force is transferred to test bay basis；
Sensor cluster includes being coaxially installed on the strain transducer 14 and piezoelectricity for determining the homonymy of frame 11 by preceding mounting flange
Sensor 15；Piezoelectric transducer uses Kistler 9317C type sensors in the present embodiment；Strain transducer structural representation is as schemed
Shown in 4, screwed hole, the end face of newel 26 and the matrix 27 of strain transducer 14 are offered on the newel 26 of strain transducer 14
Between gap be more than strain transducer design maximum range deflection, and be less than deflection corresponding to overload protection pressure value,
To ensure thrust measure precision.Demarcation flange 13 before being installed on the stress surface of strain transducer 14；Piezoelectric transducer 15 is installed
On the outside of the middle part of preceding demarcation flange 13, the head of piezoelectric transducer 15 is provided with experiment pinboard 16；On preceding demarcation flange 13
4 anti-drop rods 17 are installed, this 4 anti-drop rods 17 are through corresponding anticreep hole on experiment pinboard 16, and anti-drop rod 17 and anti-
Do not contacted between de- hole, to ensure measurement accuracy；The outside of experiment pinboard 16 prevents experiment from turning using the locking of locking nut 18
Fishplate bar 16 comes off；In order to further improve measurement accuracy, spring before being set between preceding demarcation flange 13 and preceding mounting flange 28
Piece 12, by preceding spring leaf 12 to demarcation component be accurately positioned, make demarcation component will not transverse shifting and can only be along thrust
Axis direction makees stress deformation movement；
Changeover module includes the switching cylinder 8, switching ring 10 and sensor pull rod 19 to connect successively；Switching cylinder 8 passes through
Switching cylinder mounting flange 7, which is fixedly mounted on, to be determined to be oppositely arranged on frame 11 and with sensor cluster, switches one end of ring 10 with cutting
The air cylinder tie rod 20 of ventilation cylinder 8 is threadedly coupled, and switches the other end of ring 10 and one end pivot bush unit of sensor pull rod 19, sensing
The newel screwed hole 25 of the other end of device pull bar 19 and strain transducer 14 is connected；For make handoff procedure it is more steady,
Quickly, in the present embodiment, switching ring 10 is cylindrical shape, and its one end being socketed with sensor pull rod 19 offers 60 ° of internal taper holes 30,
One end that sensor pull rod 19 is socketed with switching ring 10 has the conical surface being adapted with 60 ° of internal taper holes.
Demarcating component includes preceding demarcation flange 13, rear demarcation flange 5, demarcation cylinder mounting seat 23, demarcation cylinder 1, standard
Force snesor 2 and being fixedly mounted on determines 8 support bars 22 on the outside of frame；Demarcation flange 5 is arranged on by rear mounting flange 29 afterwards
Determine the outside of frame 11, be oppositely arranged with preceding demarcation flange 13；Demarcate between flange 5 and preceding demarcation flange 13 and drawn by 4 demarcation afterwards
Bar 9 is connected to carry out the transmission of power；Demarcation cylinder mounting seat 23 is fixed on by 8 support bars 22 determines the outside of frame 11, and with it is rear
Demarcation flange 5 be arranged in parallel；Cylinder 1 is demarcated to be arranged in demarcation cylinder mounting seat 23；Standard force snesor 2 is arranged on demarcation gas
The head of cylinder 1, and be connected by demarcating drawstring 4 with rear demarcation flange 5；Equally, in order to further improve measurement accuracy, in rear mark
Determine spring leaf 6 after being set between flange 5 and rear mounting flange 29, demarcation component is accurately positioned by rear spring leaf 6, made
Demarcation component will not transverse shifting and can only be moved along thrust axis direction as stress deformation；Can be on rear spring leaf 6 during assembling
Foil gauge is pasted on lower left and right directions, the technique adjustment of assembling process is carried out by the measurement to foil gauge, it is front and rear so as to ensure
Axiality between flange.
Cylinder control is used to control switching cylinder 8 and demarcation cylinder 1 to act；Scene need to provide 2.5MPa's during use
Clean gas；Charge amplifier is the corollary apparatus of piezoelectric transducer 15, for receiving the charge data of piezoelectric transducer 15, and it is defeated
Go out to acquisition system；Acquisition system is used for the output data for gathering standard force snesor, strain transducer 14 and charge amplifier；
The data that data handling system gathers to acquisition system are handled, and obtain attitude control engine stable state thrust and dynamic thrust.Electricity
Lotus amplifier, cylinder control, acquisition system, data handling system are existing unit.
In order to further improve measurement accuracy, the present invention is also employing heat-proof device 24 by sensor cluster and high temperature ring
Border is isolated, and the heat-proof device 24 includes thermal insulation layer housing and the water collar being arranged in thermal insulation layer housing；Thermal insulation layer inner chamber
Thickness is at least 8mm to increase thermal capacity；Thermal insulation layer housing outer surface is polished to increase heat reflection；Water collar is to sensing
Device assembly surrounding environment carries out pressure cooling；The heat-proof device 24 of the present invention can avoid heat radiation and shutdown tempering from surveying thrust
The influence of amount, the environment temperature of sensor cluster is controlled at 25 ± 1 DEG C.Shown in its structure as Fig. 5 and Fig. 6.
The course of work of the present invention：
1st, stable state is demarcated：
The head movement of control demarcation cylinder 1, translate force through demarcation route and pass to the surface of strain transducer 14 to its application
Pressure, while obtain the output of standard force snesor 2 and strain transducer 14；The output valve of reference standard force snesor 2 obtains
The linear characteristic coefficient of strain transducer 14, so as to complete the calibrated in situ of measuring system.
2nd, measure：
Needed to select strain transducer 14 or piezoelectric transducer 15 to carry out different thrust performances according to different programs
Measurement；Specially：
(1) when needing to use strain transducer 14 to carry out stable state thrust measurement, control switching cylinder 8, which acts, causes switching
Ring 10 travels forward, and switching ring 10 is departed from sensor pull rod 19, and now strain transducer 14 is in running order；When starting
When machine works, thrust magnitude is delivered to strain transducer 14 by piezoelectric transducer 15 as a rigid member in thrust transmittance process
Measure on end face, so as to obtain stable state thrust data.
(2) when needing to use piezoelectric transducer 15 to carry out dynamic thrust measurement, control switching cylinder 8, which acts, causes switching
Ring 10 tenses with sensor pull rod 19, the lower surface of newel 26 of strain transducer 14 is contacted with the upper surface of matrix 27 and is adjacent to
(as shown in Figure 4), lasting pulling force make strain transducer 14 turn into a rigid member, and one is provided for the work of piezoelectric transducer 15
Rigid basis；When engine is worked with short time impulse form, piezoelectric transducer 15 can receive the change of thrust completely
Change state, without because part force value is delivered on strain transducer 14 and influenceed to dynamic characteristic by the transmission that power occurs
Measurement.
Quasi dynamic thrust measurement calibration integrated apparatus reason provided by the present invention is applicable and the attitude control of any thrust range
Engine, physical dimension, the selection device parts of device are rationally set according to attitude control engine thrust range during practical application
Material.In the present embodiment, non-standard (in addition to sensor) material in apparatus structure uses 1Cr18Ni9Ti, is applied to
25~600N attitude control engines.
Claims (9)
1. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine, it is characterised in that：Including determining frame (11), mounting seat
(21), sensor cluster, changeover module, demarcation component, charge amplifier, cylinder control, acquisition system and data processing
System；
It is described to determine frame (11) and be fixedly mounted in the mounting seat (21)；The mounting seat (21), which is used to realize, determines frame (11) and appearance
Control the connection of engine testsand；
The sensor cluster includes being coaxially installed on the strain sensing for determining frame (11) homonymy by preceding mounting flange (28)
Device (14) and piezoelectric transducer (15)；Demarcation flange (13), strain sensing before being provided with the stress surface of strain transducer (14)
Newel screwed hole (25) is offered on the newel (26) of device (14)；Piezoelectric transducer (15) is arranged on the preceding demarcation flange
(13) on the outside of middle part, the head of piezoelectric transducer (15) is provided with experiment pinboard (16)；Before described on demarcation flange (13)
More anti-drop rods (17) are provided with, the anti-drop rod (17) tests corresponding anticreep hole on pinboard (16), and the two through described
Between do not contact；The outside of the experiment pinboard (16) carries out anticreep, locking nut (18) using locking nut (18) locking
Do not contacted with experiment pinboard (16)；
The changeover module includes the switching cylinder (8), switching ring (10) and sensor pull rod (19) to connect successively；The switching
Cylinder (8) by switch cylinder mounting flange (7) be arranged on it is described determine on frame (11), and relative with the sensor cluster set
Put；One end of switching ring (10) is connected with the air cylinder tie rod (20) of switching cylinder (8), the other end and sensor of switching ring (10)
One end pivot bush unit of pull bar (19)；The other end of sensor pull rod (19) and the newel (26) of the strain transducer (14)
It is threadedly coupled at newel screwed hole (25) place；
The demarcation component includes the preceding demarcation flange (13), demarcates flange (5), demarcation cylinder mounting seat (23), demarcation afterwards
Cylinder (1), standard force snesor (2) and more support bars (22)；Flange (5) is demarcated afterwards to be arranged on by rear mounting flange (29)
It is described to determine on the outside of frame (11), it is oppositely arranged with the preceding demarcation flange (13)；Afterwards demarcate flange (5) and it is preceding demarcate flange (13) it
Between by more demarcation pull bars (9) be connected；One end of the more support bars (22) is fixed by the rear mounting flange (29)
Installed in frame (11) outside is determined, the demarcation cylinder mounting seat (23) is fixedly mounted in the other end；Demarcate cylinder mounting seat (23) with
Demarcation flange (5) be arranged in parallel after described；Cylinder (1) is demarcated to be arranged in demarcation cylinder mounting seat (23)；Standard force snesor
(2) head of demarcation cylinder (1) is arranged on, and is connected by demarcating drawstring (4) with the rear demarcation flange (5)；
The cylinder control is used to control the switching cylinder (8) and demarcation cylinder (1) action；
The charge amplifier is used for the charge data for receiving the piezoelectric transducer (15), and is output to the acquisition system；
The acquisition system is used for the output number for gathering the standard force snesor, strain transducer (14) and charge amplifier
According to；
The data that the data handling system gathers to acquisition system are handled, and obtain attitude control engine stable state thrust and dynamic
Thrust.
2. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 1, it is characterised in that：
Before described preceding spring leaf (12) is provided between demarcation flange (13) and preceding mounting flange (28).
3. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 1 or 2, its feature exist
In：After described rear spring leaf (6) is provided between demarcation flange (5) and rear mounting flange (29).
4. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 3, it is characterised in that：
Gap is more than strain and passed between newel (26) end face of the strain transducer (14) and the matrix (27) of strain transducer (14)
The deflection of the design maximum range of sensor, and it is less than deflection corresponding to overload protection pressure value.
5. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 4, it is characterised in that：
The switching ring (10) is cylindrical shape, and one end of itself and sensor pull rod (19) socket offers 60 ° of internal taper holes (30)；Sensor
Pull bar (19) has the conical surface being adapted with 60 ° of internal taper holes with one end of switching ring (10) socket.
6. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 5, it is characterised in that：
The both ends of the demarcation drawstring (4) are connected with standard force snesor (2) and rear demarcation flange (5) respectively by draw ring (3).
7. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 6, it is characterised in that：
The anti-drop rod (17) has 4, and the support bar (22) has 8.
8. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 7, it is characterised in that：
The demarcation drawstring (4) is steel wire rope.
9. the Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine according to claim 8, it is characterised in that：
It is described to determine frame (11) and the mounting seat (21) is integrated part.
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| CN201710936008.2A CN107860504B (en) | 2017-10-10 | 2017-10-10 | Accurate dynamic thrust of appearance accuse engine measures calibration integrated device |
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| CN108562396A (en) * | 2018-07-02 | 2018-09-21 | 北京航天试验技术研究所 | A kind of live calibration device suitable for piezoelectric type thrust vectoring frame |
| CN109357881A (en) * | 2018-11-30 | 2019-02-19 | 西安航天动力测控技术研究所 | A kind of abnormity motor power measuring device |
| CN109374161A (en) * | 2018-11-30 | 2019-02-22 | 合肥中科离子医学技术装备有限公司 | A kind of pulling force acquisition device for superconducting magnet pull rod |
| CN110319972A (en) * | 2019-07-01 | 2019-10-11 | 中航工程集成设备有限公司 | A kind of Whole Process Simulation vector engine thrust calibration device |
| CN110716503A (en) * | 2019-10-10 | 2020-01-21 | 西安航天动力试验技术研究所 | High-precision thrust servo controller |
| CN112378561A (en) * | 2020-11-25 | 2021-02-19 | 西安航天动力试验技术研究所 | Integrated equipment and method for attitude control engine thrust measurement and in-situ calibration |
| CN112924157A (en) * | 2021-04-02 | 2021-06-08 | 广西玉柴机器股份有限公司 | Pressure calibration device and method for engine part mechanism |
| CN116754129A (en) * | 2023-08-09 | 2023-09-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | Structure additional resistance correction method for aero-engine bench |
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| CN108562396A (en) * | 2018-07-02 | 2018-09-21 | 北京航天试验技术研究所 | A kind of live calibration device suitable for piezoelectric type thrust vectoring frame |
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| CN110716503A (en) * | 2019-10-10 | 2020-01-21 | 西安航天动力试验技术研究所 | High-precision thrust servo controller |
| CN112378561A (en) * | 2020-11-25 | 2021-02-19 | 西安航天动力试验技术研究所 | Integrated equipment and method for attitude control engine thrust measurement and in-situ calibration |
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| CN116754129A (en) * | 2023-08-09 | 2023-09-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | Structure additional resistance correction method for aero-engine bench |
| CN116754129B (en) * | 2023-08-09 | 2023-11-17 | 中国航空工业集团公司北京长城计量测试技术研究所 | Structure additional resistance correction method for aero-engine bench |
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